81 FR 26103 - Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 84 (May 2, 2016)

We are superseding airworthiness directive (AD) 2014-12-51 for Airbus Helicopters (previously Eurocopter France) Model EC130B4 and EC130T2 helicopters. AD 2014-12-51 required repetitively inspecting the tailboom to Fenestron junction frame (junction frame) for a crack. This new AD retains the requirements of AD 2014-12-51, changes the applicability from helicopters with certain hours time-in-service (TIS) to junction frames with certain hours TIS, and adds a compliance time for sling cycles to the junction frame inspection interval. The actions of this AD are intended to detect a crack and to prevent failure of the junction frame, which could result in loss of the Fenestron and subsequent loss of control of the helicopter.

[Federal Register Volume 81, Number 84 (Monday, May 2, 2016)]
[Rules and Regulations]
[Pages 26103-26106]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-09235]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3970; Directorate Identifier 2015-SW-006-AD; 
Amendment 39-18497; AD 2016-08-20]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding airworthiness directive (AD) 2014-12-51 for 
Airbus Helicopters (previously Eurocopter France) Model EC130B4 and

[[Page 26104]]

EC130T2 helicopters. AD 2014-12-51 required repetitively inspecting the 
tailboom to Fenestron junction frame (junction frame) for a crack. This 
new AD retains the requirements of AD 2014-12-51, changes the 
applicability from helicopters with certain hours time-in-service (TIS) 
to junction frames with certain hours TIS, and adds a compliance time 
for sling cycles to the junction frame inspection interval. The actions 
of this AD are intended to detect a crack and to prevent failure of the 
junction frame, which could result in loss of the Fenestron and 
subsequent loss of control of the helicopter.

DATES: This AD is effective June 6, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of June 6, 2016.

ADDRESSES: For service information identified in this final rule, 
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, 
TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at http://www.airbushelicopters.com/techpub. You may review 
the referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort 
Worth, TX 76177. It is also on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3970.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3970; or in person at the Docket Operations Office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the European Aviation Safety Agency (EASA) AD, any 
incorporated-by-reference service information, the economic evaluation, 
any comments received, and other information. The street address for 
the Docket Operations Office (phone: 800-647-5527) is U.S. Department 
of Transportation, Docket Operations Office, M-30, West Building Ground 
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, Rotorcraft Directorate, FAA, 
10101 Hillwood Pkwy, Fort Worth, TX 76177; email [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    On September 25, 2015, at 80 FR 57742, the Federal Register 
published our notice of proposed rulemaking (NPRM) to amend 14 CFR part 
39 to remove AD 2014-12-51, Amendment 39-17921 (79 FR 45335, August 5, 
2014), and add a new AD. AD 2014-12-51 applied to Airbus Helicopters 
Model EC130B4 and EC130T2 helicopters with 690 or more hours TIS and 
required, within 10 hours TIS, dye-penetrant inspecting certain areas 
of the junction frame for a crack. AD 2014-12-51 also required, at 
intervals not exceeding 25 hours TIS, either repeating the dye-
penetrant inspection or performing a borescope inspection of certain 
areas of the junction frame for a crack. If there was a crack, AD 2014-
12-51 required replacing the junction frame. AD 2014-12-51 was prompted 
by two incidents of crack propagation through the junction frame that 
initiated in the lower right-hand side between the web and the flange 
where the lower spar of the tailboom is joined. The cracks were 
significant in length and not visible from the outside of the 
helicopter.
    The NPRM was prompted by AD No. 2015-0033-E dated February 24, 2015 
(AD 2015-0033-E), issued by EASA, which is the Technical Agent for the 
Member States of the European Union, to correct an unsafe condition on 
Airbus Helicopters EC130B4 and EC130T2 helicopters. The NPRM proposed 
to require retaining the dye penetrant and borescope inspections in AD 
2014-12-51 but with revised compliance times. The NRPM also proposed to 
change the applicability to helicopters with 690 hours TIS accumulated 
on the junction frame instead of on the helicopter, and proposed 
including an inspection interval defined in sling cycles. These actions 
were intended to detect a crack and to prevent failure of the junction 
frame, which could result in loss of the Fenestron and subsequent loss 
of control of the helicopter.

Comments

    After our NPRM (80 FR 57742, September 25, 2015) was published, we 
received a comment from one commenter.

Request

    One commenter requested the addition of a 10-hour or 250-sling 
cycle visual pilot check for helicopters with Modification 350A087421 
or that have complied with Airbus Helicopters Service Bulletin No. 
EC130-53-029, Revision 0, dated February 20, 2015 (SB EC130-53-029). 
The commenter stated this pilot check would benefit operators and 
provide the same level of safety.
    We disagree. While the EASA AD allows the check requested by the 
commenter as an alternative method, because the cause of the fatigue 
cracking is still under investigation, we cannot determine that this 
method would correct the unsafe condition.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD because we evaluated all 
information provided by EASA, reviewed the relevant information, 
considered the comment received, and determined the unsafe condition 
exists and is likely to exist or develop on other helicopters of the 
same type designs and that air safety and the public interest require 
adopting the AD requirements as proposed.

Interim Action

    We consider this AD to be an interim action. If final action is 
later identified, we might consider further rulemaking then.

Differences Between This AD and the EASA AD

    The EASA AD includes alternate compliance instructions for 
helicopters modified with a cut-out in production by Airbus Helicopters 
Modification 350A087421 or in service by compliance with SB EC130-53-
029. This AD does not.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Helicopters Emergency Alert Service Bulletin No. 
05A017, Revision 2, dated February 20, 2015 (EASB 05A017), for Model 
EC130B4 and EC130T2 helicopters. EASB 05A017 describes alternate 
procedures for inspecting outside the tailboom for a crack at reduced 
inspection intervals in combination with the internal inspections at 
extended intervals. EASB 05A017 also specifies adding sling cycles to 
the existing flight hour inspection interval for helicopters that 
perform external load-carrying operations. EASA issued AD No. 2015-
0033-E mandating the requirements in EASB 05A017 to ensure the 
continued airworthiness of these helicopters.
    This service information is reasonably available because the 
interested parties have access to it through their normal

[[Page 26105]]

course of business or by the means identified in the ADDRESSES section.

Other Related Service Information

    Airbus Helicopters also issued SB EC130-53-029, which contains 
procedures to cut out the skin and splice at the junction frame to 
facilitate the external inspection specified in EASB 05A017.

Costs of Compliance

    We estimate that this AD affects 208 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD. At an average labor rate of $85 per work-hour, 
dye-penetrant inspecting the junction frame will require 1 work-hour, 
for a cost of $85 per helicopter and a total cost of $17,680 for the 
U.S. fleet, per inspection cycle. Borescope inspecting the junction 
frame will require 0.5 work-hour, for a cost of $43 per helicopter and 
a total cost of $8,944 for the U.S. fleet, per inspection cycle.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on helicopters identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction; and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2014-12-51, Amendment 39-17921 (79 FR 45335, August 5, 2014), and 
adding the following new AD:

2016-08-20 Airbus Helicopters (Previously Eurocopter France): 
Amendment 39-18497; Docket No. FAA-2015-3970; Directorate Identifier 
2015-SW-006-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model EC130B4 and EC130T2 
helicopters with a tailboom to fenestron junction frame (junction 
frame) that has 690 or more hours time-in-service (TIS), 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the junction 
frame. This condition could result in failure of the junction frame, 
which could result in loss of the Fenestron and subsequent loss of 
control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2014-12-51, Amendment 39-17921 (79 FR 
45335, August 5, 2014).

(d) Effective Date

    This AD becomes effective June 6, 2016.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(f) Required Actions

    (1) Before the junction frame reaches 700 hours TIS or within 10 
hours TIS, whichever occurs later, remove the horizontal stabilizer, 
clean the junction frame, and dye-penetrant inspect around the 
circumference of the junction frame for a crack in the areas shown 
in Figure 1 of Airbus Helicopters EC130 Emergency Alert Service 
Bulletin No. 05A017, Revision 2, dated February 20, 2015 (EASB 
05A017). Pay particular attention to the area around the 4 spars 
(item b) of Figure 1 of EASB 05A017. An example of a crack is shown 
in Figure 3 of EASB 05A017.
    (2) Within 25 hours TIS or 390 sling cycles, whichever occurs 
first after the inspection required by paragraph (f)(1) of this AD, 
and thereafter at intervals not exceeding 25 hours TIS or 390 sling 
cycles, whichever occurs first, either perform the actions of 
paragraph (f)(1) of this AD or, if the area is clean, using a 
borescope, inspect around the circumference of the junction frame 
for a crack in the areas shown in Figure 2 of EASB 05A017. Pay 
particular attention to the area around the 4 spars (item b) of 
Figure 2 of EASB 05A017. An example of a crack is shown in Figure 3 
of EASB 05A017. For purposes of this AD, a sling cycle is defined as 
one landing with or without stopping the rotor or one external load-
carrying operation; an external load-carrying operation occurs each 
time a helicopter picks up an external load and drops it off.
    (3) If there is a crack, before further flight, replace the 
junction frame.

(g) Special Flight Permits

    Special flight permits are prohibited.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5110; email [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office, before operating any aircraft 
complying with this AD through an AMOC.

(i) Additional Information

    (1) Airbus Helicopters Service Bulletin No. EC130-53-029, 
Revision 0, dated February 20, 2015, which is not incorporated by 
reference, contains additional information about the subject of this 
final rule. For service information identified in this final rule, 
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand 
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax 
(972) 641-3775; or at http://www.airbushelicopters.com/techpub. You 
may review a copy of the service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 
6N-321, Fort Worth, TX 76177.

[[Page 26106]]

    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2015-0033-E, dated February 24, 2015. 
You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2015-3970.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 5302: Rotorcraft 
Tailboom.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Helicopters Emergency Alert Service Bulletin No. 
05A017, Revision 2, dated February 20, 2015.
    (ii) Reserved.
    (3) For Airbus Helicopters service information identified in 
this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum 
Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 
232-0323; fax (972) 641-3775; or at http://www.airbushelicopters.com/techpub.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on April 15, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-09235 Filed 4-29-16; 8:45 am]
 BILLING CODE 4910-13-P